EP1966107A2 - Gelötete verbindung zwischen einem metallteil auf titanbasis und einem keramischen teil auf basis von siliciumcarbid (sic) und/oder kohlenstoff - Google Patents

Gelötete verbindung zwischen einem metallteil auf titanbasis und einem keramischen teil auf basis von siliciumcarbid (sic) und/oder kohlenstoff

Info

Publication number
EP1966107A2
EP1966107A2 EP06842128A EP06842128A EP1966107A2 EP 1966107 A2 EP1966107 A2 EP 1966107A2 EP 06842128 A EP06842128 A EP 06842128A EP 06842128 A EP06842128 A EP 06842128A EP 1966107 A2 EP1966107 A2 EP 1966107A2
Authority
EP
European Patent Office
Prior art keywords
assembly according
ceramic material
metal part
brazing
piece
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP06842128A
Other languages
English (en)
French (fr)
Other versions
EP1966107B1 (de
Inventor
Joël Michel BENOIT
Jean-François FROMENTIN
Olivier Gillia
Lucas Domergue
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Commissariat a lEnergie Atomique et aux Energies Alternatives CEA
Original Assignee
Commissariat a lEnergie Atomique CEA
SNECMA Moteurs SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Commissariat a lEnergie Atomique CEA, SNECMA Moteurs SA filed Critical Commissariat a lEnergie Atomique CEA
Publication of EP1966107A2 publication Critical patent/EP1966107A2/de
Application granted granted Critical
Publication of EP1966107B1 publication Critical patent/EP1966107B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
    • C04B37/02—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles
    • C04B37/023—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used
    • C04B37/025—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used consisting of glass or ceramic material
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
    • C04B37/02—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles
    • C04B37/023—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used
    • C04B37/026—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used consisting of metals or metal salts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2311/00—Metals, their alloys or their compounds
    • B32B2311/18—Titanium
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5216—Inorganic
    • C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
    • C04B2235/5244—Silicon carbide
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5216—Inorganic
    • C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
    • C04B2235/5248—Carbon, e.g. graphite
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
    • C04B2237/12—Metallic interlayers
    • C04B2237/125—Metallic interlayers based on noble metals, e.g. silver
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/36—Non-oxidic
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/36—Non-oxidic
    • C04B2237/365—Silicon carbide
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
    • C04B2237/385—Carbon or carbon composite
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/40—Metallic
    • C04B2237/403—Refractory metals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/211—Silica
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/224—Carbon, e.g. graphite
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • F05D2300/2261—Carbides of silicon
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05004—Special materials for walls or lining
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12576—Boride, carbide or nitride component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736—Al-base component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31678—Of metal

Definitions

  • the present invention relates to the field of assembly by brazing of a metallic piece of titanium and a piece of ceramic material based on silicon carbide (SiC) and / or carbon.
  • ceramic materials are characterized by their mechanical properties which make them suitable for constituting structural elements and by their capacity to maintain these mechanical properties at high temperature. These materials are used in particular for the manufacture of parts undergoing high thermomechanical stresses in aeronautical applications (engine parts or fairing elements).
  • connection between ceramic materials and metals is traditionally done by a mechanical connection of the riveting or bolting type, connection sometimes unsuitable for reasons of space or difficulties of implementation.
  • the known brazing techniques used for homogeneous ceramic / ceramic bonds can hardly be used for heterogeneous brazing of ceramic material on metal because of the very different thermomechanical and chemical behaviors of ceramic materials and metals.
  • the greater relative shrinkage of the metal part generates high stresses in the two parts and in particular a zone in compression, respectively in traction, in the zones adjacent to the solder joint of the ceramic part, respectively of the metal part.
  • the invention proposes to solve the aforementioned problem by interposing, between the metal part and the part made of ceramic material, spacers with progressive coefficient of expansion thus constituting a stack of elements to be assembled thermally two by two by brazing.
  • the main object of the present invention is therefore to solve these problems by proposing an assembly which makes it possible on the one hand to compensate for the difference in expansion between the metal part and the ceramic part and, on the other hand, to avoid or limit the formation of undesirable chemical compounds.
  • the invention relates to an assembly between a metallic piece based on titanium and a piece made of ceramic material based on silicon carbide and / or carbon.
  • This assembly comprises a stacked structure comprising the following elements assembled in pairs by brazing:
  • first spacer able to deform to accommodate a differential expansion between the metal part and the part made of ceramic material
  • a second rigid interlayer with a coefficient of expansion close to that of the part made of ceramic material, aluminum nitride or tungsten, and
  • the invention therefore proposes to interpose between the ceramic and metallic parts two intermediate parts having distinct functions.
  • the first intermediate piece makes it possible to compensate for the differences in expansion between the ceramic and metallic pieces, by deforming.
  • the deformation of this part is obtained by producing the latter in a ductile metal.
  • the piece of massive structure forms a layer of ductile material capable of elongating / shrinking between the ceramic and metallic pieces.
  • the first spacer is preferably made of substantially pure titanium.
  • the first spacer is constituted by a deformable structure ("compliant" in English).
  • this structure comprises at least one intermediate connecting element assembled by brazing to the metal part and to the second intermediate, the intermediate connecting element consisting of a deformable sheet having brazed flat areas and deformable areas.
  • this deformable structure is constituted by at least one part whose general shape is that of a ribbon folded in an accordion defining curved parts turned alternately towards the metal part and towards the second interlayer, the curved parts being separated by ridges, the assembly by brazing between the first interlayer on the one hand and the metal part or the second interlayer on the other hand being produced on a flat area of at least some of the ridges.
  • the second intermediate piece has, first of all, a coefficient of expansion lower than that of the first metallic intermediate piece and preferably sufficiently close to that of the ceramic piece, in order to limit the differences in expansion between these pieces.
  • the second intermediate piece acts as a chemical barrier by preventing the migration of metallic elements towards the ceramic piece, which makes it possible to avoid the formation of fragile chemical compounds, detrimental to the good performance of the assembly.
  • this second intermediate piece can be chosen to be sufficiently elastic to allow the mechanical stresses exerted on the ceramic piece to be attenuated and sufficiently rigid to allow the mechanical stresses exerted on the ceramic piece to be distributed, which makes it possible to mechanically protect this piece which, by nature, is generally fragile.
  • the metal part consists of an alloy based on titanium, aluminum and vanadium. This alloy is called "TA6V”.
  • the coefficient of expansion of the TA6V alloy, at 500 ° C., is equal to 10.5.10 "6 K " 1 ⁇ 15%.
  • the part made of ceramic material is formed from solid or monolithic silicon carbide.
  • This material can in particular be obtained by sintering powder or granules of silicon carbide.
  • the ceramic matrix can be single-phase, for example be made entirely of SiC.
  • the matrix can alternatively be multi-phase, the matrix containing for example a sequence of alternating layers of different rigidities based on sintered silicon carbide and / or carbon pyrolysis and which can also comprise at least one self-healing phase such as a base layer boron silicon carbide Si-BC.
  • the part made of ceramic material comprises a ceramic matrix reinforced with carbon or silicon carbide fibers, in particular with a layer of silicon carbide on the surface.
  • this matrix can comprise at least one self-healing phase.
  • a ceramic material hereinafter called "A410”
  • A410 a process for obtaining this ceramic material are described in the French patent application published under the number 0 FR 2 732 338.
  • the coefficient of expansion of the material "A410", at 500 ° C., is equal to 4.0.10 "6 K " 1 ⁇ 15%.
  • the part made of ceramic material is a part made of thermostructural material comprising a fibrous carbon fiber reinforcement and a sequenced matrix with alternating layers of relatively flexible material capable of deflecting any cracks which reach them and of layers relatively rigid ceramic material.
  • A500 Such a material, hereinafter called “A500”, can be obtained by a production process such as that described in patent application FR 2 742 433.
  • the coefficient of expansion of the compound "A500”, at 500 ° C., is equal to 2.5.10 "6 K " 1 ⁇ 15%.
  • the piece of ceramic material being very brittle, it is necessary that the second interlayer is able to absorb the forces and that its coefficient of expansion is close to the piece of ceramic material. Also, the inventors have advantageously retained, for this second interlayer, very rigid aluminum nitride (AIN) or tungsten (W) and with expansion coefficients very slightly greater than that of ceramic.
  • AIN aluminum nitride
  • W tungsten
  • the coefficient of expansion of tungsten W and of aluminum nitride, at 500 ° C., are respectively equal to 5.0.10 "6 K " 1 ⁇ 15% and 5.2.10 "6 K " 1 ⁇ 15%.
  • the solder used must be reactive, which means that it must react with at least one of the chemical elements of the facing materials.
  • the solder used is a silver-based solder.
  • this solder is of the Ag-Cu-Ti or Ag-Mn type.
  • the weight percentage of silver is at least equal to 50% and the weight percentage of titanium is preferably chosen between 0.01% and 6%.
  • This solder is indeed very reactive with aluminum, tungsten and silicon, including for small proportions of titanium.
  • the Ag-Cu-Ti brazing selected by the invention comprises in weight percentages: 63 Ag, 35.25 Cu and 1.75 Ti.
  • This brazing has the advantage of being commercially available under the name CuSiI-ABA (trade name).
  • the weight percentage of manganese is preferably chosen between 1% and 25%, the proportion of manganese being explained by the fact that manganese has reactive properties with the abovementioned elements a little less than that of titanium.
  • the invention also relates to a turbomachine nozzle comprising at least one assembly as mentioned above in which the metal part is a casing (or a lever) of this nozzle and the part made of ceramic material is a flap of this nozzle.
  • the invention also relates to a turbomachine combustion chamber comprising at least one assembly as mentioned above in which the metal part is a casing (or a seal - that is to say a connecting element - or a part) of this chamber and the part made of ceramic material a component part of this chamber.
  • the invention also relates to turbomachine post-combustion equipment comprising at least one assembly as mentioned above in which the metal part is an after-combustion casing (or a platform) and the part made of ceramic material is an arm flame catcher.
  • the invention also relates to a turbomachine comprising at least one assembly as mentioned above.
  • FIG. 1 shows an assembly according to a first embodiment of the invention
  • FIG. 2 shows an assembly according to the invention in a second embodiment.
  • Figure 1 shows an assembly according to the invention in a first embodiment. It consists mainly of four parts assembled two by two by brazing, namely:
  • a second spacer 12 made of aluminum nitride AIN or tungsten W.
  • the metal part 10 is a plate or plate made of an alloy based on titanium, aluminum and vanadium (TA6V).
  • the part made of ceramic material 20 may consist of a plate or plate of monolithic (or solid) silicon carbide, or of material "A410" or "A500” as mentioned above.
  • the piece of ceramic material 20 is a composite material with a ceramic matrix.
  • This ceramic matrix can be single-phase - for example entirely made of SiC - or multiphase, for example additionally containing at least one phase with self-healing property as described in patent FR 2,732,338.
  • the CMC material consists of a fibrous carbon reinforcement and a sequenced ceramic matrix, alternating relatively flexible layers capable of deflecting cracks and layers of rigid ceramic material. It is recalled that such a material is here called “A500”. It can be obtained by a production process as described in patent application FR 2,742,433.
  • thermo-structural composite materials include: carbon / carbon composites (C / C) and ceramic matrix composites (CMC) such as C / SiC or SiC / SiC (carbon fiber reinforcement or SiC and matrix silicon carbide) or C / C-SiC (carbon fiber reinforcement and mixed carbon matrix and silicon carbide) or C / Si-BC (carbon fiber reinforcement and self-healing matrix) or C / C-SiC -Si (composite C / C silicided by reaction with Si).
  • C / C carbon / carbon composites
  • CMC ceramic matrix composites
  • CMC such as C / SiC or SiC / SiC (carbon fiber reinforcement or SiC and matrix silicon carbide) or C / C-SiC (carbon fiber reinforcement and mixed carbon matrix and silicon carbide) or C / Si-BC (carbon fiber reinforcement and self-healing matrix) or C / C-SiC -Si (composite C / C silicided by reaction with Si).
  • the first part 11 has a massive structure. This part 11 is then made of sufficiently ductile material to deform and thus compensate for the difference in expansion between the metallic and ceramic parts.
  • the dimensions of this first intermediate piece 11 and, in particular, its thickness, must be sufficient for this part to be able to play its role of deformable part without reaching excessively large deformations.
  • the first spacer 11 is made of substantially pure titanium, T40. T30 or T60 could also be used.
  • Table 1 below groups together six assemblies in accordance with Figure 1 described above.
  • the composition (A410 or A500) of the piece of ceramic material 20, the composition (AIN or W) of the second interlayer 12, the composition (T40, substantially pure titanium) of the first interlayer 11 and the composition are respectively given.
  • alloy of titanium, aluminum and vanadium TA6V of the metal part 10.
  • This brazing consists either of an Ag-Mn type brazing (Mn 15%), or of an Ag-Cu-Ti type brazing (63 Ag; 35.25 Cu; 1.75 Ti).
  • an AgZr solder Zr 3%) could be used.
  • these assemblies were subjected to shear tests using a test piece comprising a symmetrized assembly: CMC part / W or AIN insert / Ti insert / titanium-based metal part / Ti insert / W or AIN insert. / CMC piece.
  • the end pieces made of CMC materials have been immobilized in lateral jaws, while the metal piece in the center is subjected to a transverse force, which generally exerts shear stresses in the two intermediate zones between each end piece in CMC and the central metal part, at the level of the spacers.
  • shear strength of assembly # 1 is equal to 50% of the shear strength of material A500.
  • the shear strength of the assembly obtained according to the invention reaches or even exceeds (in the most favorable cases) the shear strength of the part made of CMC material. This constitutes a decisive quality for such mechanical assembly (resistance of the joint reaching a value equal to or greater than the assembled parts).
  • FIG. 2 represents another assembly in accordance with the invention, in which the first insert 11 ′ is constituted by a deformable structure ("compiling" in English).
  • the intermediate piece 11 ′ can be formed by a deformable sheet 16 comprising concentric undulations and flat areas 14 arranged alternately on the opposite ridges of the undulations, or on only some of these ridges. These flat areas 14 are brazed alternately, according to their orientation, either on the metal part 10 or on the second insert 12.
  • this deformable structure 11 ' is constituted by a part whose general shape is that of a ribbon folded in accordion defining curved parts turned alternately towards the metal part 10 and towards the second interlayer 12.
  • the assembly of the invention can be implemented in a turbomachine and, more particularly, in a turbojet engine.
  • the metal part 10 can belong to a casing of the turbojet engine and said ceramic part can be: a nozzle flap, a part of the combustion chamber or a post-combustion flame catching arm.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Products (AREA)
EP06842128.8A 2005-12-08 2006-12-08 Gelötete verbindung zwischen einem metallteil auf titanbasis und einem keramischen teil auf basis von siliciumcarbid (sic) und/oder kohlenstoff Active EP1966107B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0553788A FR2894498B1 (fr) 2005-12-08 2005-12-08 Assemblage par brasage entre une piece metallique a base de titane et une piece en materiau ceramique a base de carbure de silicium (sic) et/ou de carbone
PCT/FR2006/051317 WO2007066051A2 (fr) 2005-12-08 2006-12-08 Assemblage par brasage entre une piece metallique a base de titane et une piece en materiau ceramique a base de carbure de silicium (sic) et/ou de carbone

Publications (2)

Publication Number Publication Date
EP1966107A2 true EP1966107A2 (de) 2008-09-10
EP1966107B1 EP1966107B1 (de) 2018-02-07

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EP06842128.8A Active EP1966107B1 (de) 2005-12-08 2006-12-08 Gelötete verbindung zwischen einem metallteil auf titanbasis und einem keramischen teil auf basis von siliciumcarbid (sic) und/oder kohlenstoff

Country Status (8)

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US (1) US8161753B2 (de)
EP (1) EP1966107B1 (de)
JP (1) JP5200283B2 (de)
CN (1) CN101326140B (de)
CA (1) CA2632712C (de)
FR (1) FR2894498B1 (de)
RU (1) RU2416587C2 (de)
WO (1) WO2007066051A2 (de)

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EP2233835A1 (de) * 2009-03-23 2010-09-29 Siemens Aktiengesellschaft Mit Keramikeinsätzen hartgelötete Brennkammer
EP2492444A1 (de) * 2011-02-22 2012-08-29 General Electric Company Metall-Keramik-Fügeverfahren für Gasturbinen durch Metallisierung eines Teils aus Keramik-Matrix-Verbundwerkstoff
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FR3095150B1 (fr) 2019-04-16 2021-07-16 Commissariat Energie Atomique Procede d’assemblage d’une piece en carbone et d’une piece metallique en deux etapes
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Also Published As

Publication number Publication date
RU2416587C2 (ru) 2011-04-20
WO2007066051A2 (fr) 2007-06-14
JP5200283B2 (ja) 2013-06-05
WO2007066051A3 (fr) 2007-08-02
CA2632712C (fr) 2013-09-10
US20090068004A1 (en) 2009-03-12
RU2008127504A (ru) 2010-01-20
CN101326140B (zh) 2012-07-04
JP2009519880A (ja) 2009-05-21
CN101326140A (zh) 2008-12-17
US8161753B2 (en) 2012-04-24
FR2894498B1 (fr) 2009-07-10
FR2894498A1 (fr) 2007-06-15
CA2632712A1 (fr) 2007-06-14
EP1966107B1 (de) 2018-02-07
WO2007066051B1 (fr) 2007-09-13

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